Performance of the Integrated Gas and Steam Cycle (IGSC) for Reheat Gas Turbines

In 1978, the Japanese government started a national project for energy conservation called the Moonlight Project. The Engineering Research Association for Advanced Gas Turbines was selected to research and develop an advanced gas turbine for this project. The development stages were planned as follows: First, the development of a reheat gas turbine for a pilot plant (AGTJ-100A), and second, a prototype plant (AGTJ-100B). The AGTJ-100A has been undergoing performance tests since 1984 at the Sodegaura Power Station of the Tokyo Electric Power Co., Inc. (TEPCO). The inlet gas temperature of the high pressure turbine (HPT) of the AGTJ-100A is 1573K, while that of the AGTJ-100B is 100K higher. Therefore, various advanced technologies have to be applied to the AGTJ-100B HPT. Ceramic coating on the HPT blades is the most desirable of these technologies. In this paper, the present situation of development, as well as future R & D plans for ceramic coating, is taken into consideration. Steam blade cooling is applied for the IGSC.

A High Performance PFB System for Utility Application

In the traditional pressurized fluid bed (PFB) power system, the PFB is located in the highest pressure portion of the power cycle, Figure 1. This results in the smallest volume flow through the PFB, but also requires the combustion products to flow through the entire expansion train. This is not expected to be a major problem when the PFB temperature is limited to 1600°F for effective sulfur capture and to avoid alkali vapors in the products of combustion. However, when topping combustion is added ahead of the turbine so as to reach state-of-the-art turbine inlet temperatures, a major risk for turbine corrosion and fouling develops.

Application of the Transient Test Technique to Measure Local Heat Transfer Coefficients Associated With Augmented Airfoil Cooling Passages

The failure of a turbine airfoil is a local phenomena. However, to date, the design of these airfoils has been based on steady state heat transfer tests that are capable of yielding only locally averaged data. To overcome this limitation, a transient technique using active surface coatings has been developed and is capable of yielding local data. This technique has been used to determine the Nusselt number distributions within augmented passages typical of gas turbine airfoils. However, certain assumptions have been made in these analyses without verification. This paper will address this aspect of the problem, as well as an improved data reduction procedure, and an alternative error analysis. The data reduction procedure has been improved by incorporating a higher order approximation to the convective boundary condition, and by introducing a means of calculating the fluid bulk temperature-time-space profile. An image analysis system which yields an unbiased means of determining the time required for the surface to reach a specified temperature is introduced. Furthermore, it was observed that for augmented surfaces, the one dimensional conduction assumption made in the heat transfer solution is not valid for all times. Finally, treating the experimentally obtained quantities as values that are randomly distributed about some true value is not correct for all experimentally measured quantities.

Blade Temperature Measurements of Model V84.2 100 MW/60 Hz Gas Turbine

Numerous experimental investigations have been performed with a model V84.2 100 MW / 60 Hz gas turbine up to peak load conditions. The paper presents an overview of the most interesting experiments. In detail, pyrometric measurements of the first stage turbine blade are described and discussed. Surface temperature distributions are presented in the form of contour plots, and a comparison with theoretical predictions is shown exemplarily. Moreover, the effect of turbulence promoters on the cooling channel side walls is demonstrated.

Thermodynamic Study of an Indirect Fired Air Turbine Cogeneration System With Regeneration

A previous study of an indirect fired air turbine cogeneration system has been extended to include the concept of regeneration. The effect of regenerator effectiveness and full regeneration as well as partial regeneration on system performance parameters (such as fuel utilization efficiency, power-to-heat ratio and second-law efficiency) are examined. An important conclusion of this study is that a regenerative gas turbine cogeneration system is capable of producing large power-to-heat ratios for various process conditions requiring the use of only moderate compressor compression ratio and moderately effective regenerators. It appears that this is an attractive system which could compete in a market that is currently dominated by internal combustion engines when a viable fludized bed air heater is available.

Aspects of Gas Turbine Noise Control in the Vicinity of Residential Areas

This paper deals with problems of noise control involving gas turbine plants, particularly where they are installed near residential areas already subject to noise nuisance. Noise control measures for existing industrial or power-generating plant are often designed to achieve an overall immitted noise level only marginally below the legal maximum. Considerably enhanced measures are thus required for additional plant. However, the noise from a gas turbine plant has numerous individual sources and it is shown that a differentiated approach is required. Generally, progressive reductions in noise levels involve disproportionately greater increases in expenditure on appropriate measures. Stringent environmental protection requirements necessitate cost-intensive solutions.

Computation of Full-Coverage Film-Cooled Airfoil Temperatures by Two Methods and Comparison With High Heat Flux Data

Two methods were used to calculate the heat flux to full-coverage film cooled airfoils and, subsequently, the airfoil wall temperatures. The calculated wall temperatures were compared to measured temperatures obtained in the Hot Section Facility operating at real engine conditions. Gas temperatures and pressures up to 1900 K and 18 atm with a Reynolds number up to 1.9 million were investigated. Heat flux was calculated by the convective heat transfer coefficient adiabatic wall method and by the superposition method which incorporates the film injection effects in the heat transfer coefficient. The results of the comparison indicate the first method can predict the experimental data reasonably well. However, superposition overpredicted the heat flux to the airfoil without a significant modification of the turbulent Prandtl number. The results of this research suggests that additional research is required to model the physics of full-coverage film cooling where there is significant temperature/density differences between the gas and coolant.

Part Load Performance of the Intercooled Two-Shaft Gas Turbine With Power Output at Constant Speed on the High-Pressure Shaft

The general analysis of the part load performance of gas turbines indicates that the intercooled cycle with two shafts and power output at constant speed on the high-pressure shaft can have a good part load efficiency. Calculations with fixed geometry of the turbomachines show an intolerable increase of the turbine inlet temperature above the permissible level. By introducing variable geometry in the turbomachines, this disadvantage can be overcome. With variable inlet guide vanes at the high-pressure compressor an excellent part load performance is achieved. Further improvements are possible by adding an internal heat exchanger.

Boosting Steam Plant Thermal Efficiency and Power Output Through the Addition of Gas Turbines

This paper describes the conversion of existing conventional steam power plants into combined cycle plants. A number of Dutch utility companies are currently performing or planning this conversion on their gas-fired power stations, mainly in order to conserve fuel. Modifications of boiler and steam cycle, necessary for the new concept, are presented in general terms, together with a detailed description of one of the projects.

Applying Kalina Technology to a Bottoming Cycle for Utility Combined Cycles

A new power generation technology often referred to as the Kalina cycle, is being developed as a direct replacement for the Rankine steam cycle. It may be applied to any thermal heat source, low or high temperature. Among several Kalina cycle variations there is one that is particularly well suited as a bottoming cycle for utility combined cycle applications. It is the subject of this paper. Using an ammonia/water mixture as the working fluid and a condensing system based on absorption refrigeration principles the Kalina bottoming cycle outperforms a triple pressure steam cycle by 16 percent. Additionally, this version of the Kalina cycle is characterized by an intercooling feature between turbine stages, diametrically opposite to normal reheating practice in steam plants. Energy and mass balances are presented for a 200 MWe Kalina bottoming cycle. Kalina cycle performance is compared to a triple pressure steam plant. At a peak cycle temperature of 950° F the Kalina plant produces 223.5 MW vs. 192.6 MW for the triple pressure steam plant, an improvement of 16.0 percent. Reducing the economizer pinch point to 15° F results in a performance improvement in excess of 30 percent.